NO. 3 



APPENDIX 



.1H7 



DATA SHEET No. 11. 



Weight of Aerodrome N<^. 5, Superposed Wings and P6naud Rudder. 



Certified to bj Chas. M. Manly, August 3, 1899. 



Sizes. 



Frame, including everything of metal, permanent and 

 undetachable, such as bed-plate, cro ■ i ids for the 

 support of propellers, bearing points for - Lutch, etc 



Engine, complete 



Pump, 301; pump shaft, 55; Bupporl to pump, S3 



Hull covering, 276; apron, 117; piece behind separator 



Gasoline and air tanks, 107, 105; air valve, 17 



Smokestack and piece to protect midrod 



Float, 2'."'. drop piece for rudder, 57; guy-post and 

 clamp, 17 



Red, fork and float, 128; ateam gauge with pipe, si 



Wing clamps, 202; guy-post clamps, 33 



Boiler, 775; burner, 171; counter, l«w> 



Rear extension to midrod 



Separator and pipes to engine and pump 



Exhaust pipe 



Front lower bearing points, 84; clutch post, 41 



Rear bearing points, 1JG; extra strengthened, 8'2 



Wings (without clamp) 



Tail (without clamp), part of rudder 



Rudder 



Guy sticks, each 60 



Propellers, 100 em. round end 



Extra lentcth of midrod, front 



Wood bowsprit 



Other things, 24S grammes of lead on end of bowsprit. 



Fuel (at starting flight)... 

 \\ ater (at starting Bight). 



Sundries unknown . 

 Total flying weight . 



Total area of support (not including tail) sq.ft. 



Total area of support in feet, divided by total flying 



weight in lhs 



Total area of horizontal tail sq.ft. 



Total area of rudder (vertical) sq. ft, 



Horse-power at brake Horse-power by formula* 



Lift at pendulum (during one minute absolute) 



Lift ;ii pendulum (during one minute in terms of wt.). 



Minimum pressure with which wheels turn 



Position of center of pressure of wings f 



Curvature of wings, l in 11. 

 Root angle of wings, 10°.... 



Tip angle of wings, 10° 



Position of wings 



How guyed 



Position of tail 



Angle of tail 



Co-efficient elasticity of tail, 200 grammes at enter gives 



deflection of 5° 



P- .sit inn of rudder 



Elasticity caused by robber bands 



Line of thrust, 1500 



(enter of gravityi of whole 



("'enter of gravity;.. 



Center of pressure! of whule estimate 



Center of pressure™ 



70 

 71 



72 



Weight 



K7.5 



2.75 



6.94 

 7.64 



3666 

 470 

 889 

 393 

 349 

 StiEj 



304 

 809 

 L'35 

 1040 

 227 

 613 

 90 

 325 

 178 



309 

 120 

 757 

 174 



130 

 248 



14,354 





G '.' on F. \v.. 1677/ 



Line through center of propellers, 

 1500. 



C of G. t 1498. 



C. P. on R. W., 137U.7. 



Rev. x diam. X pilch ratio -■■ thrust 

 "' r ' 33000 



t This is calculated on the assumption that the center of pressure on each wing or on pair of wings at a motion of 2000 feet per 

 minuteisin . - curved ; wings 2-5 the v.,: h nn fi >nt to rear, that for wings of usual size the rear win; of the 



Xiene^p'r uV,,',,,, ,1. and that the tail proper bears no pari ... tl ^er or large, 



this efficiency is smaller or larger per unit of surface. 



